Title (fr)

Publication

Application

Priority

DE 19719197 A 19970509

Abstract (en)

[origin: EP0877156A2] To operate the combustion chamber of a gas turbine assembly, using liquid fuel, the liquid fuel (38) is evaporated in a separate evaporator reactor (12) in at least two steps. Initially, the liquid fuel (38) is brought into indirect contact with an initial heat exchange medium (21) for sputtering as a mixture of liquid and vapour fuel. Part of the liquid fuel (38) is abruptly vaporised, and the remainder of the liquid fuel (38) is evaporated by direct contact with a heat exchange medium (51). Also claimed is an assembly with a vertical evaporation reactor (12) upstream of the mixing stretch (56) of the combustion chamber (2), with a connection (11) to it. It has a liquid fuel feed (19) and a feed (20) for the initial heat exchange medium (21) with a twin-material jet (22). The evaporation reactor (12) has a pressure body and a mantle tube, with a feed and an exhaust channel (49,50) for a second heat exchange medium (51), leading into a ring channel between the pressure body and mantle. The jet (22), for two materials, has a tubular inner body and an outer mantle, forming a ring gap between them.